USA 26 AIRFOIL (usa26-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: USA 26 AIRFOIL (usa26-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.71 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa26-il-1000000-n5.txt Download as CSV file: xf-usa26-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 26 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4155 0.13039 0.12868 -0.0239 1.0000 0.0068
-12.500 -0.4115 0.12790 0.12621 -0.0242 1.0000 0.0070
-12.000 -0.8293 0.02588 0.02305 -0.0884 0.9825 0.0112
-11.750 -0.8163 0.02332 0.02023 -0.0878 0.9796 0.0119
-11.500 -0.7925 0.02225 0.01908 -0.0879 0.9782 0.0127
-11.250 -0.7672 0.02130 0.01803 -0.0883 0.9770 0.0136
-11.000 -0.7429 0.01999 0.01653 -0.0886 0.9760 0.0144
-10.750 -0.7161 0.01904 0.01544 -0.0891 0.9752 0.0151
-10.500 -0.6824 0.01921 0.01567 -0.0902 0.9746 0.0156
-10.250 -0.6565 0.01951 0.01604 -0.0895 0.9714 0.0161
-10.000 -0.6263 0.01973 0.01631 -0.0898 0.9692 0.0167
-9.750 -0.5976 0.01935 0.01586 -0.0903 0.9673 0.0173
-9.500 -0.5689 0.01858 0.01497 -0.0910 0.9657 0.0179
-9.250 -0.5398 0.01772 0.01395 -0.0917 0.9644 0.0185
-9.000 -0.5097 0.01705 0.01316 -0.0926 0.9631 0.0189
-8.750 -0.4819 0.01670 0.01273 -0.0927 0.9610 0.0192
-8.500 -0.4622 0.01594 0.01186 -0.0914 0.9560 0.0197
-8.250 -0.4336 0.01567 0.01155 -0.0916 0.9530 0.0201
-7.750 -0.3693 0.01549 0.01135 -0.0935 0.9481 0.0208
-7.500 -0.3456 0.01557 0.01144 -0.0925 0.9402 0.0212
-7.250 -0.3133 0.01515 0.01093 -0.0936 0.9327 0.0216
-7.000 -0.2886 0.01461 0.01028 -0.0930 0.9224 0.0220
-6.750 -0.2608 0.01425 0.00982 -0.0931 0.9125 0.0226
-6.500 -0.2336 0.01371 0.00915 -0.0930 0.9005 0.0231
-6.250 -0.2075 0.01311 0.00840 -0.0927 0.8868 0.0235
-6.000 -0.1815 0.01270 0.00785 -0.0923 0.8686 0.0239
-5.750 -0.1566 0.01242 0.00739 -0.0916 0.8458 0.0242
-5.500 -0.1337 0.01210 0.00690 -0.0905 0.8194 0.0244
-5.250 -0.1110 0.01179 0.00642 -0.0893 0.7971 0.0245
-5.000 -0.0878 0.01151 0.00601 -0.0882 0.7771 0.0247
-4.750 -0.0651 0.01122 0.00557 -0.0871 0.7563 0.0248
-4.500 -0.0424 0.01099 0.00520 -0.0859 0.7318 0.0249
-4.250 -0.0210 0.01084 0.00487 -0.0844 0.6974 0.0249
-4.000 -0.0017 0.01037 0.00417 -0.0826 0.6553 0.0253
-3.750 0.0171 0.01022 0.00375 -0.0807 0.6000 0.0256
-3.500 0.0382 0.01008 0.00343 -0.0792 0.5599 0.0263
-3.250 0.0615 0.00998 0.00321 -0.0782 0.5361 0.0269
-3.000 0.0857 0.00987 0.00301 -0.0774 0.5193 0.0273
-2.750 0.1103 0.00977 0.00283 -0.0766 0.5059 0.0277
-2.250 0.1604 0.00959 0.00254 -0.0753 0.4834 0.0287
-2.000 0.1854 0.00951 0.00240 -0.0746 0.4727 0.0291
-1.750 0.2104 0.00944 0.00227 -0.0739 0.4619 0.0296
-1.500 0.2356 0.00938 0.00215 -0.0733 0.4504 0.0301
-1.250 0.2608 0.00931 0.00204 -0.0726 0.4410 0.0304
-1.000 0.2860 0.00928 0.00195 -0.0720 0.4312 0.0309
-0.750 0.3113 0.00923 0.00187 -0.0714 0.4215 0.0313
-0.500 0.3365 0.00921 0.00179 -0.0708 0.4123 0.0316
-0.250 0.3617 0.00920 0.00174 -0.0701 0.4027 0.0320
0.000 0.3870 0.00919 0.00170 -0.0695 0.3942 0.0324
0.250 0.4118 0.00917 0.00163 -0.0688 0.3856 0.0343
0.500 0.4371 0.00916 0.00161 -0.0682 0.3779 0.0373
0.750 0.4621 0.00917 0.00161 -0.0676 0.3704 0.0406
1.000 0.4874 0.00917 0.00161 -0.0670 0.3640 0.0467
1.250 0.5122 0.00920 0.00163 -0.0663 0.3567 0.0560
1.500 0.5372 0.00918 0.00164 -0.0657 0.3513 0.0736
1.750 0.5598 0.00904 0.00168 -0.0646 0.3439 0.1637
2.000 0.5840 0.00904 0.00174 -0.0639 0.3367 0.1986
2.250 0.6083 0.00904 0.00181 -0.0632 0.3298 0.2364
2.500 0.6327 0.00908 0.00189 -0.0625 0.3242 0.2647
2.750 0.6574 0.00908 0.00197 -0.0618 0.3195 0.3003
3.000 0.6819 0.00909 0.00205 -0.0612 0.3154 0.3350
3.250 0.7042 0.00899 0.00215 -0.0601 0.3110 0.4242
3.750 0.7767 0.00804 0.00258 -0.0642 0.3038 0.9677
4.000 0.8098 0.00818 0.00270 -0.0654 0.3002 0.9743
4.250 0.8466 0.00837 0.00286 -0.0675 0.2957 0.9797
4.500 0.8787 0.00853 0.00301 -0.0685 0.2893 0.9852
4.750 0.9161 0.00873 0.00316 -0.0708 0.2810 0.9880
5.000 0.9495 0.00888 0.00330 -0.0721 0.2749 0.9904
5.250 0.9790 0.00908 0.00345 -0.0727 0.2644 0.9925
5.500 1.0077 0.00927 0.00360 -0.0731 0.2527 0.9943
5.750 1.0374 0.00969 0.00383 -0.0739 0.2179 0.9959
6.000 1.0595 0.01069 0.00442 -0.0735 0.1486 0.9979
6.250 1.0874 0.01118 0.00478 -0.0740 0.1263 0.9992
6.500 1.1130 0.01166 0.00512 -0.0739 0.1029 1.0000
6.750 1.1200 0.01258 0.00575 -0.0701 0.0526 1.0000
7.000 1.1288 0.01334 0.00635 -0.0665 0.0185 1.0000
7.250 1.1452 0.01364 0.00666 -0.0643 0.0144 1.0000
7.500 1.1615 0.01395 0.00698 -0.0621 0.0127 1.0000
7.750 1.1773 0.01427 0.00733 -0.0598 0.0110 1.0000
8.000 1.1938 0.01456 0.00765 -0.0577 0.0105 1.0000
8.250 1.2100 0.01487 0.00799 -0.0556 0.0099 1.0000
8.500 1.2245 0.01518 0.00832 -0.0531 0.0094 1.0000
8.750 1.2372 0.01550 0.00867 -0.0502 0.0089 1.0000
9.000 1.2490 0.01590 0.00909 -0.0473 0.0081 1.0000
9.250 1.2616 0.01631 0.00954 -0.0445 0.0076 1.0000
9.500 1.2757 0.01670 0.00997 -0.0422 0.0074 1.0000
9.750 1.2899 0.01711 0.01042 -0.0399 0.0071 1.0000
10.000 1.3036 0.01757 0.01092 -0.0376 0.0068 1.0000
10.250 1.3173 0.01805 0.01144 -0.0354 0.0065 1.0000
10.500 1.3304 0.01858 0.01200 -0.0332 0.0062 1.0000
10.750 1.3433 0.01913 0.01259 -0.0310 0.0060 1.0000
11.000 1.3538 0.01984 0.01336 -0.0286 0.0057 1.0000
11.250 1.3626 0.02066 0.01425 -0.0260 0.0054 1.0000
11.500 1.3723 0.02146 0.01511 -0.0237 0.0054 1.0000
11.750 1.3844 0.02215 0.01585 -0.0218 0.0052 1.0000
12.000 1.3959 0.02289 0.01664 -0.0199 0.0049 1.0000
12.250 1.4037 0.02389 0.01771 -0.0177 0.0048 1.0000
12.500 1.4127 0.02486 0.01874 -0.0158 0.0047 1.0000
12.750 1.4197 0.02601 0.01997 -0.0139 0.0045 1.0000
13.000 1.4271 0.02720 0.02121 -0.0122 0.0044 1.0000
13.250 1.4328 0.02857 0.02266 -0.0105 0.0043 1.0000
13.500 1.4376 0.03009 0.02426 -0.0090 0.0042 1.0000
13.750 1.4406 0.03187 0.02611 -0.0076 0.0041 1.0000
14.000 1.4424 0.03387 0.02818 -0.0064 0.0040 1.0000
14.250 1.4427 0.03613 0.03053 -0.0055 0.0039 1.0000
14.500 1.4383 0.03904 0.03355 -0.0048 0.0039 1.0000
14.750 1.4331 0.04228 0.03689 -0.0045 0.0038 1.0000
15.000 1.4249 0.04612 0.04085 -0.0048 0.0037 1.0000
15.250 1.4208 0.04970 0.04454 -0.0053 0.0036 1.0000
15.500 1.4113 0.05415 0.04912 -0.0063 0.0037 1.0000
15.750 1.4100 0.05755 0.05262 -0.0070 0.0036 1.0000
16.000 1.3984 0.06243 0.05761 -0.0083 0.0036 1.0000
16.250 1.3799 0.06829 0.06360 -0.0098 0.0036 1.0000
16.500 1.3738 0.07244 0.06785 -0.0109 0.0035 1.0000
16.750 1.3628 0.07734 0.07285 -0.0122 0.0036 1.0000
17.000 1.3541 0.08194 0.07754 -0.0135 0.0035 1.0000
17.250 1.3353 0.08814 0.08385 -0.0155 0.0036 1.0000
17.500 1.3306 0.09227 0.08807 -0.0167 0.0034 1.0000
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